EP0730212A2 - Steueranordnung eines handgesteuerten Flugzeugsystemes mit insbesondere einem Head-Up-Display - Google Patents

Steueranordnung eines handgesteuerten Flugzeugsystemes mit insbesondere einem Head-Up-Display Download PDF

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Publication number
EP0730212A2
EP0730212A2 EP96400346A EP96400346A EP0730212A2 EP 0730212 A2 EP0730212 A2 EP 0730212A2 EP 96400346 A EP96400346 A EP 96400346A EP 96400346 A EP96400346 A EP 96400346A EP 0730212 A2 EP0730212 A2 EP 0730212A2
Authority
EP
European Patent Office
Prior art keywords
screen
displays
information
indicator
landing
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP96400346A
Other languages
English (en)
French (fr)
Other versions
EP0730212A3 (de
EP0730212B1 (de
Inventor
Ron Ching
J.R. Lawren B. Webster
François Faivre
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Thales Avionics SAS
Original Assignee
Thales Avionics SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Thales Avionics SAS filed Critical Thales Avionics SAS
Publication of EP0730212A2 publication Critical patent/EP0730212A2/de
Publication of EP0730212A3 publication Critical patent/EP0730212A3/de
Application granted granted Critical
Publication of EP0730212B1 publication Critical patent/EP0730212B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • G—PHYSICS
    • G05—CONTROLLING; REGULATING
    • G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
    • G05D1/00—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
    • G05D1/04—Control of altitude or depth
    • G05D1/06—Rate of change of altitude or depth
    • G05D1/0607—Rate of change of altitude or depth specially adapted for aircraft
    • G05D1/0653—Rate of change of altitude or depth specially adapted for aircraft during a phase of take-off or landing
    • G05D1/0676—Rate of change of altitude or depth specially adapted for aircraft during a phase of take-off or landing specially adapted for landing

Definitions

  • the present invention relates to a device for controlling an aircraft system with manual piloting, in particular using a head-up collimator. It applies in particular to allow control of a manual landing or takeoff from the right seat, that of a co-pilot for example, in the cockpit of an airplane.
  • landing collimators for approaches to manual piloting is done more and more frequently, including in poor visibility, thus for example in bad weather corresponding to a level of category 3A as defined by aeronautical regulations.
  • This information is in particular trajectory guidance orders developed from ILS or equivalent signals.
  • control parameters to be presented to the co-pilot are defined in various regulations, in particular the known regulations AC 120-28C. These regulations essentially require the co-pilot to be shown the vertical speed of the aircraft and excessive deviations from the ILS beam.
  • the object of the invention is to eliminate these drawbacks by a particular presentation of the symbols at the level of the right place.
  • the subject of the invention is a device for controlling an aircraft system with manual piloting, characterized in that it consists of a display screen situated in place of a piece of equipment. right of the dashboard, the screen displaying the information delivered by the replaced equipment and / or the information necessary for piloting control when using a collimator.
  • the main advantages of the invention are that it improves safety, that it simplifies the replacement or addition of systems on already existing dashboards, that it simplifies the training of pilots and that it is simple to enforce.
  • Figure 1 shows, as an example, a Category 3A certified system for manual landing. It consists of at least a first aircraft system 1 and a second aircraft system 2 connected to a computer 3 supplying signals to a head-up collimator 4. The system also comprises a screen 5 connected to the first aircraft system 1 and to the computer 3. This screen 5 acts as a control instrument for the co-pilot.
  • FIG. 2 shows a dashboard portion 20 located on the right side of the cockpit and provided with conventional equipment.
  • This part notably includes a radio altimeter 21, a speedometer 22 and an ADI 23.
  • ADI Integrated Access Management Function
  • Adding a landing control instrument to this dashboard 20 is a complex and costly operation. In particular, this requires modifying the ADI, replacing one of the aforementioned devices 21, 22 and other equipment 24 with a scrolling system, adding an alarm and mode button. In addition, all the additional information necessary for the landing control is scattered, which does not promote safety.
  • the principle of the invention consists in replacing one of the abovementioned items of equipment 21, 22 of the dashboard with a screen having the function of the item of equipment replaced and landing control indication information such as for example that defined in the regulation AC 120-28C.
  • the device according to the invention is a display screen 31 situated in place of the vertical speed indicator 22.
  • This screen is for example connected to the first aircraft system 1 and to the computer 3 as defined with reference to FIG. 3.
  • the electronic instrument reproduces the replaced instrument. In this case, it presents a typical indicator image 22.
  • the other function provided by the control device is intended for controlling the landing.
  • the screen 31 displays for example an indication of landing approach control. It can also display take-off and taxi information. All these indications are in particular specified in the regulation AC 120-28C.
  • the device can function for example as a vertical speed indicator meeting the FAR 135 standard, that is to say that it presents in conventional form, with needles, the measurement of the vertical speed developed from pressure variations according to whether the plane is going up or down.
  • Screen 31 displays this conventional configuration, for example during operations in good visibility called VMC according to the English expression "Visual Meteorological Condition". This configuration symbolizes, for example, the shape of the vertical speed indicator illustrated in FIG. 2.
  • the screen 31 always displays the vertical speed indication so in particular that the device retains its function of vertical speedometer.
  • this information is presented in digital form, as illustrated for example by the value 600 displayed in the embodiment shown in Figure 3.
  • the measurement of this vertical speed is for example developed from a baro-inertial measurement loop coupling a measurement of vertical acceleration and atmospheric pressure.
  • the acceleration measurement is for example acquired at the output of the aircraft inertial unit.
  • the device according to the invention can, for example, meet the requirements for category 3A approach certification.
  • requirements for category 3A approach certification include the presentation of information and alarms to the co-pilot, also known as PNF, according to the English expression "Pilot Non Flying". This information and alarms make it possible in particular to guarantee the smooth running of the approach and the flare.
  • the co-pilot must be able to detect and prevent a round that is too long or too short.
  • FIG. 4 shows an example of display of the screen 31. This display is for example triggered by an approach in IMC mode.
  • an indicator 44 of radio altimeter height which represents, for example in the form of a ribbon, the altitude.
  • the darker surface of the bottom 44 ′ goes up, for example, to the center of the ribbon 44, thus giving excellent information on the rounding speed.
  • the screen 31 presents for example by an indicator 45 the rounding height.
  • the radio altimeter is for example directly controlled to avoid common mode errors.
  • the screen On its left side, the screen may for example have an indicator 46 for vertical deviation.
  • the position of this indicator 46 on a scale 47 makes it possible in particular to present the guide deviations to the co-pilot.
  • These deviations can either directly present the so-called ILS deviations, that is to say the deviations from the vertical approach axis, or the guiding error between the speed vectors, defining the trajectory, and the guiding order. developed by the calculator.
  • the location scale 48 can be presented, for example, which presents with improved resolution the gross deviations in lateral position of the aircraft with respect to the location signal.
  • the enlargement of the location scale can be done with a variable factor to take into account the different requirements of landing and take-off. Common mode errors are avoided by directly using signals from the ILS receiver.
  • the guidance symbols 49, 50 can for example be represented.
  • the speed vector 50 and the guidance order 49 are written in a square 51 which can, for example, represent the maximum allowable deviations.
  • an APCH WRN 43 alarm is triggered, for example.
  • the background color of the square 51 can then change to red so as to indicate a particular procedure called "go around".
  • the vertical speed is presented in alphanumeric form and indicates the instantaneous vertical speed at the output of the inertial system.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Automation & Control Theory (AREA)
  • Traffic Control Systems (AREA)
EP96400346A 1995-03-02 1996-02-20 Steueranordnung eines handgesteuerten Flugzeugsystemes mit insbesondere einem Head-Up-Display Expired - Lifetime EP0730212B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US39735195A 1995-03-02 1995-03-02
US397351 1995-03-02

Publications (3)

Publication Number Publication Date
EP0730212A2 true EP0730212A2 (de) 1996-09-04
EP0730212A3 EP0730212A3 (de) 1997-04-23
EP0730212B1 EP0730212B1 (de) 2003-01-22

Family

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Family Applications (1)

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EP96400346A Expired - Lifetime EP0730212B1 (de) 1995-03-02 1996-02-20 Steueranordnung eines handgesteuerten Flugzeugsystemes mit insbesondere einem Head-Up-Display

Country Status (4)

Country Link
US (1) US5808563A (de)
EP (1) EP0730212B1 (de)
CA (1) CA2170851C (de)
DE (1) DE69625835T2 (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2903386A1 (fr) * 2006-07-06 2008-01-11 Airbus France Sas Systeme d'affichage pour aeronef.
FR2916541A1 (fr) * 2007-05-25 2008-11-28 Thales Sa Dispositif de visualisation tete haute pour aeronef comprenant des moyens d'affichage d'une symbologie dediee a l'evitement d'obstacles.

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6057786A (en) * 1997-10-15 2000-05-02 Dassault Aviation Apparatus and method for aircraft display and control including head up display
US6052069A (en) * 1997-10-29 2000-04-18 Sikorsky Aircraft Corporation Taxi and slope landing symbology for a helicopter
JP2000276206A (ja) * 1999-03-24 2000-10-06 Yamaha Motor Co Ltd 総合特性最適化方法及び装置
US6255964B1 (en) * 1999-10-28 2001-07-03 Gordon H. Steele, Jr. Universal aircraft panel with a dynamically symmetrical series of displays for the directional and rate flight instruments
FR2831871B1 (fr) * 2001-11-08 2004-08-13 Airbus France Procede et dispositif d'aide au pilotage d'un aeronef
US6946976B1 (en) * 2002-02-28 2005-09-20 Garmin International, Inc. Cockpit display systems and methods of presenting data on cockpit displays
US20070088467A1 (en) * 2005-09-27 2007-04-19 Calspan Corporation Integrated system for providing real-time assistance to aircrew
US20070142980A1 (en) * 2005-12-19 2007-06-21 Marc Ausman Avionics method and apparatus
US20080004756A1 (en) * 2006-06-02 2008-01-03 Innovative Solutions & Support, Inc. Method and apparatus for display of current aircraft position and operating parameters on a graphically-imaged chart
FR2922323B1 (fr) * 2007-10-12 2012-08-03 Airbus France Dispositif de surveillance croisee pour afficheurs dits tete haute
FR2935179B1 (fr) * 2008-08-20 2010-12-03 Airbus France Procede et dispositif d'aide au controle des systemes embarques dans un aeronef
FR2935187B1 (fr) * 2008-08-20 2010-09-17 Airbus France Procede et dispositif de partage de donnees entre des systemes embarques dans un aeronef
FR3023368B1 (fr) * 2014-07-04 2016-08-19 Airbus Operations Sas Procede et dispositif d'aide a l'atterrissage d'un aeronef.
EP3465095A1 (de) * 2016-05-31 2019-04-10 Bombardier Inc. Anzeige von leistungsbegrenzungen in einer flugzeuganzeige

Citations (8)

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US4057782A (en) * 1976-04-05 1977-11-08 Sundstrand Data Control, Inc. Low altitude head up display for aircraft
DE3546116A1 (de) * 1985-12-24 1987-06-25 Heinz Mueller Verfahren zur darstellung von soll- und istdaten des flugzustandes vor und waehrend der landung fuer einen piloten
EP0324195A2 (de) * 1988-01-15 1989-07-19 The Boeing Company Integriertes, primäres Fluganzeigeinstrument
EP0396071A2 (de) * 1989-05-02 1990-11-07 Honeywell Inc. Gerät und Methode für eine Flugzeuganzeige, die Hinweise gibt bezüglich vertikaler Geschwindigkeit, Verkehrslage und Kollisionsauflösung
EP0489521A2 (de) * 1990-12-05 1992-06-10 Smiths Industries Public Limited Company Sichtanzeigeanlagen und -systeme
EP0545473A2 (de) * 1991-12-06 1993-06-09 The Boeing Company Neigungsleit-Steuerungsgesetz für TCAS II und Symbolzeichen
US5359890A (en) * 1993-05-04 1994-11-01 Honeywell Inc. Integrated electronic primary flight display
US5382954A (en) * 1993-05-27 1995-01-17 Honeywell Inc. Resolution advisory display instrument for TCAS guidance

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US3594757A (en) * 1968-03-20 1971-07-20 Kaiser Aerospace & Electronics Waveform generator for providing tape display of continuously changing data
US3626163A (en) * 1970-01-28 1971-12-07 Us Army Automatic landing system
US4357661A (en) * 1980-02-22 1982-11-02 The Boeing Company Aircraft landing control system
US5111400A (en) * 1987-03-16 1992-05-05 Yoder Evan W Automatic integrated real-time flight crew information system
US4975696A (en) * 1987-03-23 1990-12-04 Asinc, Inc. Real-time flight and destination display for aircraft passengers
US4896154A (en) * 1987-10-28 1990-01-23 Eventide Inc. Map display system for vehicle navigation
US4914733A (en) * 1987-10-30 1990-04-03 Allied-Signal, Inc. Traffic advisory-instantaneous vertical speed display
US5043727A (en) * 1989-02-03 1991-08-27 Sanshin Kogyo Kabushiki Kaisha Display system for marine vessel
US5185606A (en) * 1990-05-08 1993-02-09 Fokker Aircraft B.V. Primary flight display presenting resolution advisory information provided by a traffic alert and collision avoidance system
US5208590A (en) * 1991-09-20 1993-05-04 Asinc, Inc. Flight phase information display system for aircraft passengers

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4057782A (en) * 1976-04-05 1977-11-08 Sundstrand Data Control, Inc. Low altitude head up display for aircraft
DE3546116A1 (de) * 1985-12-24 1987-06-25 Heinz Mueller Verfahren zur darstellung von soll- und istdaten des flugzustandes vor und waehrend der landung fuer einen piloten
EP0324195A2 (de) * 1988-01-15 1989-07-19 The Boeing Company Integriertes, primäres Fluganzeigeinstrument
EP0396071A2 (de) * 1989-05-02 1990-11-07 Honeywell Inc. Gerät und Methode für eine Flugzeuganzeige, die Hinweise gibt bezüglich vertikaler Geschwindigkeit, Verkehrslage und Kollisionsauflösung
EP0489521A2 (de) * 1990-12-05 1992-06-10 Smiths Industries Public Limited Company Sichtanzeigeanlagen und -systeme
EP0545473A2 (de) * 1991-12-06 1993-06-09 The Boeing Company Neigungsleit-Steuerungsgesetz für TCAS II und Symbolzeichen
US5359890A (en) * 1993-05-04 1994-11-01 Honeywell Inc. Integrated electronic primary flight display
US5382954A (en) * 1993-05-27 1995-01-17 Honeywell Inc. Resolution advisory display instrument for TCAS guidance

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2903386A1 (fr) * 2006-07-06 2008-01-11 Airbus France Sas Systeme d'affichage pour aeronef.
US7772995B2 (en) 2006-07-06 2010-08-10 Airbus France Display system for aircraft
FR2916541A1 (fr) * 2007-05-25 2008-11-28 Thales Sa Dispositif de visualisation tete haute pour aeronef comprenant des moyens d'affichage d'une symbologie dediee a l'evitement d'obstacles.
WO2008145590A2 (fr) * 2007-05-25 2008-12-04 Thales Dispositif de visualisation tête haute pour aéronef comprenant des moyens d'affichage d'une symbologie dédiée a l'évitement d'obstacles
WO2008145590A3 (fr) * 2007-05-25 2009-05-07 Thales Sa Dispositif de visualisation tête haute pour aéronef comprenant des moyens d'affichage d'une symbologie dédiée a l'évitement d'obstacles

Also Published As

Publication number Publication date
DE69625835T2 (de) 2003-11-13
US5808563A (en) 1998-09-15
CA2170851A1 (fr) 1996-09-03
EP0730212A3 (de) 1997-04-23
CA2170851C (fr) 2007-08-21
DE69625835D1 (de) 2003-02-27
EP0730212B1 (de) 2003-01-22

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